Aviation cable device for thermal resistor of gas turbine

Abstract

The invention discloses an aviation cable device for a thermal resistor of a gas turbine, belongs to the technical field of aviation cables and connectors, and is designed for solving the problems that an existing cable device is prone to unsoldering, virtual connection and the like. The invention discloses an aviation cable device for a thermal resistor of a gas turbine. The aviation cable device comprises an aviation joint; the aviation cable, the conductor and the jack part are crimped to be tightly attached and then are welded to form a connection structure of the conductor and the jack part; part of the metal wires are drawn out of all the metal wires to be welded to the grounding part, and the other metal wires are insulated and isolated from the aviation connector. According to the aviation cable device for the thermal resistor of the gas turbine, the phenomena of unsoldering and virtual connection can be obviously reduced, the stability and the reliability of a connection structure are improved, the failure rate of the aviation device using the aviation cable device is reduced, and the aviation cable device can adapt to severe working environments such as high temperature, vibration and corrosion; through independent research and development, the problem of import dependence is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation cables and connectors, and particularly to an aviation cable device for a gas turbine thermal resistor. Background Art

[0002] The cable device mainly includes a connector and a cable connected to each other. The cable is used to transmit signals, and the connector is used to connect the cable to a device for receiving signals. In order to achieve a stable connection between the connector and the cable, in the prior art, the conductors inside the cable are usually welded to the welding ends on the connector.

[0003] Aviation devices need to work in harsh environments such as high temperature, vibration, and corrosion. The welding structure between the existing connectors and cables is prone to problems such as solder joint detachment and poor connection, resulting in failures of aviation devices and poor reliability. In order to improve the stability of products, most of the existing aviation cables and connectors rely on imports, with a long procurement cycle and high costs. Summary of the Invention

[0004] The purpose of the present invention is to provide an aviation cable device for a gas turbine thermal resistor, which solves the problems of easy solder joint detachment and poor connection of the existing cable device and has high reliability.

[0005] To achieve this purpose, the present invention adopts the following technical solutions:

[0006] An aviation cable device for a gas turbine thermal resistor includes: an aviation connector provided with at least one grounding part and at least two jack parts; an aviation cable for transmitting electrical signals between the gas turbine and a control system, the aviation cable including four temperature compensation lines arranged in parallel and a heat shrinkable tube sleeve wrapping the four temperature compensation lines. Each temperature compensation line includes two conductors, a shielding layer wrapping the two conductors on the outside, and an outer sheath wrapping the shielding layer on the outside. The two conductors include a red nickel-chromium wire and a black nickel-silicon wire, and the shielding layer is used for anti-electromagnetic interference; the conductors are crimped to the jack parts until they are in close contact and then welded to form a connection structure between the conductors and the jack parts; and a wave-proof sleeve sleeved on the outside of one end of the aviation cable connected to the aviation connector, the length of the wave-proof sleeve being less than the length of the aviation cable; the wave-proof sleeve includes a wave-proof sleeve body and at least two metal wires, and a part of the metal wires are drawn out from all the metal wires and welded to the grounding part, and the remaining metal wires are insulated from the aviation connector.

[0007] In one preferred embodiment, the jack parts extend in a direction perpendicular to the bottom surface of the aviation connector, and the extending direction of the conductors is perpendicular to the bottom surface of the aviation connector.

[0008] In one preferred embodiment, the wave-proof sleeve body includes an insulating layer and a protective layer sleeved outside the insulating layer, and the protective layer is made of a material with a wear resistance exceeding a set parameter.

[0009] In one preferred embodiment, the aviation cable device further includes a protective shell connected to the aviation connector, and the protective shell is sleeved outside the connection structure between the conductor and the jack portion.

[0010] In one preferred embodiment, the protective shell is made of a material with both corrosion resistance and mechanical strength exceeding a set value.

[0011] In one preferred embodiment, a section of the bundling tube is sleeved at a set distance outside each of the four temperature compensation wires.

[0012] In one preferred embodiment, the nickel-chromium wire includes a copper conductor core inside and a nickel-chromium outer sheath wrapped outside the copper conductor core; and / or, the nickel-silicon wire includes a copper conductor core inside and a nickel-silicon outer sheath wrapped outside the copper conductor core; and / or, the heat-shrinkable tube sleeve is made of polytetrafluoroethylene; and / or, the bundling tube is made of polytetrafluoroethylene.

[0013] In one preferred embodiment, the shielding layer is woven from tinned copper wires, and the density value of the shielding layer is ≥95%.

[0014] In one preferred embodiment, the outer sheath is made of TPV.

[0015] In one preferred embodiment, the aviation cable device further includes a rubber washer and a fixing ferrule. The rubber washer is sleeved on the aviation cable, and the fixing ferrule is clamped outside the rubber washer.

[0016] For the aviation cable device for a gas turbine thermal resistor disclosed in the present invention, after the conductor and the jack portion are crimped to be closely fitted and then welded to form a connection structure between the conductor and the jack portion, the phenomenon of soldering-off and loose connection can be significantly reduced, the stability and reliability of the connection structure are both improved, the failure rate of the aviation device using the aviation cable device is reduced, and it can adapt to harsh working environments such as high temperature, vibration, and corrosion; through independent research and development, domestic products replace imported aviation cables and complete sets of spare parts for connectors, solve the problem of import dependence, reduce procurement costs and time costs, ensure supply chain security, have flexible inventory management, and significantly improve the maintenance and production efficiency of the unit. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is an exploded view of the aviation cable device provided by the specific embodiment of the present invention;

[0018] Figure 2It is a cross-sectional view of the aviation cable device provided by the specific embodiment of the present invention;

[0019] Figure 3 It is a schematic cross-sectional view of the aviation cable provided by the specific embodiment of the present invention.

[0020] In the figure:

[0021] 1. Aviation connector; 2. Aviation cable; 3. Wave-proof sleeve; 4. Protection shell; 5. Rubber washer; 6. Fixed ferrule; 11. Grounding part; 12. Jack part; 13. Dust-proof cover; 21. Temperature compensation wire; 22. Heat-shrinkable tube sleeve; 23. Cluster tube; 31. Metal wire; 211. Conductor; 212. Shielding layer; 213. Outer sheath. Specific embodiment

[0022] In order to make the above objects, features and advantages of the present invention more obvious and understandable, the following detailed description of the specific embodiments of the present invention will be given in conjunction with the accompanying drawings. Many specific details are set forth in the following description in order to fully understand the present invention. However, the present invention can be implemented in many other ways different from those described herein, and those skilled in the art can make similar improvements without departing from the connotation of the present invention. Therefore, the present invention is not limited by the specific embodiments disclosed below.

[0023] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0024] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of these features. In the description of the present invention, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0025] In the present invention, unless otherwise clearly defined or limited, terms such as "installed", "connected", "joined", "fixed", etc. shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two components or the interaction relationship between two components, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0026] In the present invention, unless otherwise clearly defined or limited, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may mean that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "underneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower horizontal height than the second feature.

[0027] It should be noted that when an element is referred to as "fixed to" or "disposed on" another element, it can be directly on the other element or there may also be an intermediate element. When an element is considered to be "connected" to another element, it can be directly connected to the other element or there may be an intermediate element at the same time. The terms "vertical", "horizontal", "up", "down", "left", "right" and similar expressions used herein are only for illustrative purposes and do not represent the only implementation.

[0028] The present embodiment discloses an aviation cable device for a gas turbine thermal resistor, which realizes the transmission of electrical signals between the gas turbine and the control system to ensure the stability and reliability of the unit operation. Among them, the gas turbine thermal resistor can be, but is not limited to, products of various models of General Electric (GE).

[0029] As Figure 1 and Figure 2 shown, the aviation cable device includes an aviation connector 1, an aviation cable 2 and a wave-proof sleeve 3. Among them, the main component for transmitting electrical signals between the gas turbine and the control system is the aviation cable 2. The aviation connector 1 includes a connector body and a dust-proof cover 13 sleeved outside the connector body. At least one grounding portion 11 and at least two jack portions 12 are provided on the connector body; the aviation cable 2 is connected to the jack portion 12, and the wave-proof sleeve 3 is sleeved outside one end of the aviation cable 2 connected to the aviation connector 1.

[0030] The aviation cable 2 includes four temperature compensation wires 21 arranged in parallel and a heat shrinkable tube sleeve 22 wrapped around the four temperature compensation wires 21. Each temperature compensation wire 21 includes two conductors 211 arranged in parallel, a shielding layer 212 wrapped around the outer sides of the two conductors 211, and an outer sheath 213 wrapped around the outer side of the shielding layer 212. The two conductors 211 include a red nickel-chromium wire and a black nickel-silicon wire, and the shielding layer 212 is used for anti-electromagnetic interference.

[0031] The wave-proof sleeve 3 includes a wave-proof sleeve body and at least two metal wires 31. Among all the metal wires 31, some of the metal wires 31 are drawn out and welded to the grounding part 11, and the remaining metal wires 31 are insulated from the aviation connector 1. In order to reduce costs and improve heat dissipation performance, the length of the wave-proof sleeve 3 is less than the length of the aviation cable 2.

[0032] The conductor 211 and the jack part 12 are crimped until they are in close fit and then welded to form a connection structure between the conductor 211 and the jack part 12, which can significantly reduce the phenomenon of soldering-off and loose connection. The stability and reliability of the connection structure are both improved, the failure rate of the aviation device using this aviation cable device is reduced, and it can adapt to harsh working environments such as high temperature, vibration, and corrosion; through independent research and development, domestic products replace imported aviation cables and complete sets of spare parts for connectors, solve the problem of import dependence, reduce procurement costs and time costs, ensure supply chain security, have flexible inventory management, and significantly improve the maintenance and production efficiency of the unit.

[0033] Among them, there is no specific limit to the specific judgment standard of "close fit", as long as it can ensure that both the electrical connection and the mechanical connection between the aviation connector 1 and the aviation cable 2 meet the requirements. In this embodiment, it can be determined that the conductor 211 and the jack part 12 are "close fit" when they are extruded under a set pressure for a set time, or it can be determined that the conductor 211 and the jack part 12 do not separate under their own weight after the pressure is removed, or it can be determined that the conductor 211 and the jack part 12 do not separate after applying a set value of tensile force to the conductor 211 after the pressure is removed. The conductor 211 and the jack part 12 need to be fitted tightly enough to make the welding reach the best effect, avoid soldering-off and loose connection, have good product consistency, long service life of this aviation cable device, and can adapt to various harsh working environments.

[0034] The specific structure of the aviation connector 1 is not limited, and it can be, but is not limited to, the JY83723 / 95G1005N plug, as long as it can meet the specification requirements of various high-performance aviation cables 2 of 2×20AWG (American wire gauge).

[0035] In this embodiment, three to five strands of the metal wires 31 are drawn out from all the metal wires 31 and welded to the grounding part 11, and the remaining metal wires 31 are cut off flush and then tied with cotton cords, and then coated with Q98-1 glue or other insulating glues to achieve insulation isolation from the aviation connector 1.

[0036] On the basis of the above structure, the jack part 12 extends in a direction perpendicular to the bottom surface of the aviation connector 1, and the extending direction of the conductor 211 is perpendicular to the bottom surface of the aviation connector 1. That is, the jack part 12 and the bottom surface of the aviation connector 1 are in an L shape. After connection, the pressure received on the conductor 211 is basically consistent with the axis of the conductor 211, reducing the radial stress received on the aviation cable 2 and prolonging the service life of the aviation cable 2.

[0037] The specific structure of the wave-proof sleeve body is not limited. In this embodiment, the wave-proof sleeve body includes an insulating layer and a protective layer sleeved outside the insulating layer. The insulating layer is made of a composite material with high temperature resistance and corrosion resistance, improving the stability of the aviation cable device in a high-temperature environment; the protective layer is made of a high-strength material with wear resistance exceeding the set parameters, enhancing the mechanical strength and anti-wear ability of the aviation cable device, and having a wider application range.

[0038] On the basis of the above structure, the aviation cable device further includes a protective shell 4 connected to the aviation connector 1. The protective shell 4 is sleeved outside the connection structure between the conductor 211 and the jack part 12, which can prevent environmental corrosion and mechanical damage, ensure the firm connection between the aviation connector 1 and the aviation cable 2, and have higher reliability.

[0039] The specific preparation material of the protective shell 4 is not limited. In this embodiment, the protective shell 4 is made of a material with corrosion resistance and mechanical strength both exceeding the set values to adapt to harsh working environments such as high temperature, vibration, and corrosion. Among them, the specific value of the "set value" is not limited and can be determined according to the use requirements.

[0040] The heat shrinkable tube sleeve 22 can restrain the four temperature compensation wires 21, avoiding the collision or entanglement of the temperature compensation wires 21 with surrounding objects. When the aviation cable 2 is relatively long or the working environment is relatively complex, a bundling tube 23 can be added inside or outside the heat shrinkable tube sleeve 22. It is only necessary to sleeved a section of bundling tube 23 at a set distance outside the four temperature compensation wires 21. The bundling tube 23 is preferably made of a heat shrinkable material, and a section of bundling tube 23 is sleeved every about one meter, which has better binding, insulation and protection effects on the temperature compensation wires 21.

[0041] The specific structures of the nickel-chromium wire and the nickel-silicon wire are not limited. In this embodiment, the nickel-chromium wire includes a copper core located inside and a nickel-chromium outer layer wrapped around the copper core; and / or, the nickel-silicon wire includes a copper core located inside and a nickel-silicon outer layer wrapped around the copper core, which can stably transmit signals, have stronger corrosion resistance and oxidation resistance, and can be applicable to the use requirements of various aviation cables 2 including the 20AWG (cross-sectional area of about 0.52mm 2 ) specification. In this embodiment, the design of the four temperature compensation wires 21 can meet the dual-channel signal transmission requirements and has a wide application range.

[0042] The heat shrinkable tube sleeve 22 is made of polytetrafluoroethylene (abbreviated as PTFE, or also known as fluoroplastics); and / or, the bundling tube 23 is made of polytetrafluoroethylene. It has good electrical insulation performance, can withstand a temperature environment of -200°C to +260°C, can effectively prevent signal leakage, and has a wide application range; it has a low dielectric constant and low loss, is suitable for high-frequency signal transmission, and has strong product competitiveness.

[0043] The specific structure of the shielding layer 212 is not limited. In this embodiment, the shielding layer 212 is woven from tinned copper wires, and the density value of the shielding layer 212 ≥ 95%, and both the corrosion resistance and the welding performance are stronger; it has the ability to resist electromagnetic interference (EMI) to ensure the stability and accuracy of signal transmission. In order to improve the ability to resist electromagnetic interference, multiple shielding layers 212 can be sleeved.

[0044] The specific structure of the outer sheath 213 is not limited. In this embodiment, the outer sheath 213 is made of TPV (an elastomer with EPDM as the main base material, formed by dynamic vulcanization, and can also be called a special elastomer), which has strong mechanical protection ability, has good wear resistance, oil resistance, and corrosion resistance, and can adapt to harsh environments; the TPV material itself has high flexibility and is easy to install and maintain.

[0045] On the basis of the above structure, the aviation cable device further includes a rubber washer 5 and a fixing collar 6. The rubber washer 5 is sleeved on the aviation cable 2, and the fixing collar 6 is clamped outside the rubber washer 5. The fixing collar 6 can prevent the aviation cable 2 from moving relative to the aviation connector 1 in the axial direction, ensuring that the connection structure between the aviation connector 1 and the aviation cable 2 is more stable; the rubber washer 5 can prevent the fixing collar 6 from scratching the outer peripheral surface of the aviation cable 2 and at the same time increase the stability of the fixing collar 6 relative to the aviation cable 2.

[0046] Note that the above is only the preferred embodiment of the present invention and the technical principles applied. Those skilled in the art will understand that the present invention is not limited to the specific embodiments described herein, and various obvious changes, re-adjustments and substitutions can be made by those skilled in the art without departing from the protection scope of the present invention. Therefore, although the present invention has been described in more detail through the above embodiments, the present invention is not limited to the above embodiments. Without departing from the concept of the present invention, more other equivalent embodiments can be included, and the scope of the present invention is determined by the scope of the appended claims.

Claims

1. An aviation cable device for a gas turbine thermal resistor, characterized in that, Comprising: An aviation connector (1) provided with at least one grounding part (11) and at least two jack parts (12); An aviation cable (2) for transmitting electrical signals between the gas turbine and the control system. The aviation cable (2) includes four temperature compensation wires (21) arranged in parallel and a heat shrinkable tube sleeve (22) wrapped around the four temperature compensation wires (21). Each temperature compensation wire (21) includes two conductors (211), a shielding layer (212) wrapped around the outside of the two conductors (211), and an outer sheath (213) wrapped around the outside of the shielding layer (212). The two conductors (211) include a red nickel-chromium wire and a black nickel-silicon wire. The shielding layer (212) is used for anti-electromagnetic interference. The conductor (211) and the jack part (12) are crimped to be closely fitted and then welded to form a connection structure between the conductor (211) and the jack part (12); and, A wave-proof sleeve (3) sleeved on the outside of one end of the aviation cable (2) connected to the aviation connector (1). The length of the wave-proof sleeve (3) is less than the length of the aviation cable (2). The wave-proof sleeve (3) includes a wave-proof sleeve body and at least two metal wires (31). Some of the metal wires (31) are drawn out and welded to the grounding part (11), and the remaining metal wires (31) are insulated from the aviation connector (1).

2. The aviation cable device for a gas turbine thermal resistor according to claim 1, characterized in that, The jack part (12) extends in a direction perpendicular to the bottom surface of the aviation connector (1), and the extending direction of the conductor (211) is perpendicular to the bottom surface of the aviation connector (1).

3. The aviation cable device for a gas turbine thermal resistor according to claim 1, characterized in that The wave-proof sleeve body includes an insulating layer and a protective layer sleeved on the outside of the insulating layer. The protective layer is made of a material with wear resistance exceeding a set parameter.

4. The aviation cable device for a gas turbine thermal resistor according to claim 1, characterized in that, The aviation cable device further includes a protective shell (4) connected to the aviation connector (1). The protective shell (4) is sleeved on the outside of the connection structure between the conductor (211) and the jack part (12).

5. The aviation cable device for a gas turbine thermal resistor according to claim 4, characterized in that, The protective shell (4) is made of a material with corrosion resistance and mechanical strength both exceeding a set value.

6. The aviation cable device for a gas turbine thermal resistor according to claim 1, wherein A section of the bundling tube (23) is sleeved on the outside of the four temperature compensation wires (21) at intervals of a set distance.

7. The aviation cable device for a gas turbine thermal resistor according to any one of claims 1 to 6, characterized in that The nickel-chromium wire includes a copper core inside and a nickel-chromium outer layer wrapped around the copper core; and / or, The nickel-silicon wire includes a copper core inside and a nickel-silicon outer layer wrapped around the copper core; and / or, The heat shrinkable tube sleeve (22) is made of polytetrafluoroethylene; and / or, The bundling tube (23) is made of polytetrafluoroethylene.

8. The aviation cable device for a gas turbine thermal resistor according to any one of claims 1 to 6, characterized in that, The shielding layer (212) is woven from tinned copper wires, and the density value of the shielding layer (212) ≥ 95%.

9. The aviation cable device for a gas turbine thermal resistor according to any one of claims 1 to 6, characterized in that, The outer sheath (213) is made of TPV.

10. The aviation cable device for a gas turbine thermal resistor according to any one of claims 1 to 6, characterized in that, The aviation cable device further includes a rubber washer (5) and a fixing collar (6). The rubber washer (5) is sleeved on the aviation cable (2), and the fixing collar (6) is clamped on the outside of the rubber washer (5).

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